Vortex Method with Gaussian Vortices for Separated Shear Flow of the Airfoil

For the analysis of the laminar separated flow around the NACA symmetrical airfoil in transition region of Reynolds number, it is a problem that the flow separation and the development of the shear layer are sensitive to the flow conditions very much. Hence, we made the matching of laminar boundary layer theory with vortex method. We also proposed a new scheme that the vorticity field in the shear layer is decided from the Gaussian vorticity distribution and the no-slip condition is adopted by setting diffusive and productive vortices. We made clear that the flow separation is estimated with laminar boundary layer theory. And Computational results around the body showed good agreement with the experimental ones